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公开(公告)号：EP3254030B1
公开(公告)日：2019-05-22
申请号：EP16706096.1
申请日：2016-02-04
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2.发明公开SYSTEMS AND METHODS FOR HIGH VOLUMETRIC OXIDANT FLOW IN GAS TURBINE ENGINE WITH EXHAUST GAS RECIRCULATION 审中-公开具有废气再循环的燃气涡轮发动机中的高体积氧化剂流动的系统和方法
公开(公告)号：EP3254032A2
公开(公告)日：2017-12-13
申请号：EP16706097.9
申请日：2016-02-04
发明人： BORCHERT, Bradford David , TROUT, Jesse Edwin , SIMMONS, Scott Robert , VALEEV, Almaz , SLOBODYANSKIY, Ilya Aleksandrovich , SIDKO, Igor Petrovich , GINESIN, Leonid Yul'evich
CPC分类号： F23R3/28 , F02C3/04 , F02C3/34 , F23C9/00 , F23C2202/50 , F23R3/002 , F23R3/10 , F23R3/286 , F23R3/30 , F23R3/32 , F23R3/343 , F23R3/346 , F23R3/36 , F23R2900/00001 , F23R2900/00005 , Y02E20/16 , Y02T50/675
摘要： A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.
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公开(公告)号：EP3254030A1
公开(公告)日：2017-12-13
申请号：EP16706096.1
申请日：2016-02-04
发明人： ALLEN, Jonathan Kay , BORCHERT, Bradford David , TROUT, JesseEdwin , SLOBODYANSKIY, Ilya Aleksandrovich , VALEEV, Almaz , SIDKO, Igor Petrovich , ROBERTS, Matthew Eugene , GINESIN, Leonid Yul'evich
CPC分类号： F02C3/34 , F01D9/023 , F05D2260/61 , F23C9/08 , F23C2202/50 , F23C2900/09001 , F23R3/005 , F23R3/04 , F23R3/26 , F23R2900/03043 , Y02T50/675
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.
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